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公开(公告)号：EP2909153B1
公开(公告)日：2018-05-30
申请号：EP13789855.7
申请日：2013-10-16
IPC分类号： C04B35/10 , C04B35/565 , C04B35/584 , B32B18/00 , C04B38/06 , F01D5/28 , C04B111/00
CPC分类号： F01D5/284 , B28B1/001 , B32B18/00 , C04B35/10 , C04B35/565 , C04B35/584 , C04B38/06 , C04B2111/00405 , C04B2235/665 , C04B2235/775 , C04B2237/343 , C04B2237/365 , C04B2237/368 , C04B2237/76 , F01D9/02 , C04B38/0074
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公开(公告)号：EP3448829B1
公开(公告)日：2020-08-19
申请号：EP17722117.3
申请日：2017-04-19
申请人： Safran
发明人： PODGORSKI, Michael , DAMBRINE, Bruno , RUIZ, Edu
IPC分类号： C04B35/117 , B28B7/34 , B28B7/36 , B28B7/46 , C04B35/14 , C04B35/18 , C04B35/185 , C04B35/447 , C04B35/488 , C04B35/56 , C04B35/565 , C04B35/58 , C04B35/584 , C04B35/626 , C04B35/80 , B29C70/44 , B29C70/02 , F01D5/28 , D03D25/00 , B01D29/05
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13.发明公开
公开(公告)号：EP3448829A1
公开(公告)日：2019-03-06
申请号：EP17722117.3
申请日：2017-04-19
申请人： Safran
发明人： PODGORSKI, Michael , DAMBRINE, Bruno , RUIZ, Edu
IPC分类号： C04B35/117 , B28B7/34 , B28B7/36 , B28B7/46 , C04B35/14 , C04B35/18 , C04B35/185 , C04B35/447 , C04B35/488 , C04B35/56 , C04B35/565 , C04B35/58 , C04B35/584 , C04B35/626 , C04B35/80 , B29C70/44 , B29C70/02 , F01D5/28 , D03D25/00 , B01D29/05
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14.发明公开
公开(公告)号：EP3359707A1
公开(公告)日：2018-08-15
申请号：EP16790656.9
申请日：2016-10-04
申请人： SAFRAN
CPC分类号： C23C30/00 , C04B41/009 , C04B41/52 , C04B41/89 , F01D5/284 , F01D5/288 , F05D2300/173 , C04B35/80 , C04B41/5096 , C04B41/5042 , C04B41/0036 , C04B41/4539 , C04B41/5031 , C04B41/5032
摘要： The invention relates to a turbine engine part (10) comprising at least one substrate (11) and one ceramic coating (12) for protection against calcium and magnesium aluminum silicates present on the substrate, the ceramic coating including Al2O3 with a molar content of between 33% and 49%, Y3Al5O12 with a molar content of between 21% and 53%, and yttria-stabilized zirconia with a molar content of between 13% and 31%. The invention also relates to a method for manufacturing such a part and to a method for using such a part.
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公开(公告)号：EP3060383A1
公开(公告)日：2016-08-31
申请号：EP14789932.2
申请日：2014-10-03
发明人： PODGORSKI, Michael , DAMBRINE, Bruno Jacques Gerard , LE HONG, Son , COUPE, Dominique Marie Christian , MOLLIEX, Ludovic Edmond, Camille , GOERING, Jonathan
CPC分类号： F01D9/02 , B29B11/16 , B29C53/02 , B29C53/04 , B29C69/001 , B29C70/24 , B29C70/48 , B29C70/545 , B29C70/546 , B29K2713/00 , B29L2031/08 , C04B35/80 , C04B2235/3217 , C04B2235/3244 , C04B2235/3418 , C04B2235/3463 , C04B2235/3826 , C04B2235/3873 , C04B2235/5216 , D03D3/02 , F01D9/041 , F01D25/005 , F05D2220/30 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/50 , F05D2300/21 , F05D2300/2112 , F05D2300/6012 , F05D2300/6033 , F05D2300/6034 , Y02T50/672 , Y02T50/673
摘要： A fiber preform for a hollow turbine engine vane, the preform comprising a main fiber structure obtained by three-dimensional weaving and including at least one main part (41), wherein the main part (41) extends from a first link strip (44p), includes a first main longitudinal portion (46) suitable for forming essentially a pressure side wall of an airfoil, then includes an U-turn bend portion (45) suitable for forming essentially a leading edge or a trailing edge of the airfoil, then includes a second main longitudinal portion (47) facing the first main longitudinal portion (46) and suitable for forming essentially a suction side wall of the airfoil, and terminating at a second link strip (44q), wherein the first and second link strips (44p, 44q) are secured to each other and form a link portion (44) of the main fiber structure, and wherein the main longitudinal portions (46, 47) are spaced apart so as to form a gap between said main longitudinal portions (46, 47) suitable for forming a hollow in the airfoil.
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